CN103691793A - Age hardenable aluminum alloy integral panel one-step forming method based on autoclave - Google Patents
Age hardenable aluminum alloy integral panel one-step forming method based on autoclave Download PDFInfo
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- CN103691793A CN103691793A CN201310711973.1A CN201310711973A CN103691793A CN 103691793 A CN103691793 A CN 103691793A CN 201310711973 A CN201310711973 A CN 201310711973A CN 103691793 A CN103691793 A CN 103691793A
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Abstract
The invention discloses an age hardenable aluminum alloy integral panel one-step forming method based on an autoclave. The method includes the steps: firstly, fixing an aluminum alloy plate blank on a forming die, and placing the aluminum alloy plate blank into the autoclave after the aluminum alloy plate blank and the forming die are sealed in a vacuum manner; secondly, providing temperature needed by aluminum alloy aging and pressure needed by component laminating inside the autoclave, and enabling heavy-curvature portion materials to reach yield limit and enter a creep aging stage by keeping a laminating state after plastic deformation. Internal stress distribution is adjusted by local plastic deformation, so that the problem of non-uniform performance caused by internal stress difference in the creep aging process can be eliminated, production cycle and rebound are decreased by combining plastic deformation with creep deformation, and the height of the die can be decreased. The process method can be implemented in the autoclave with enough capacity, the highest working pressure is not lower than 10Bar, and the using temperature can range from 100 DEG C to 200 DEG C. The method is simple and convenient to operate, can be implemented only by one set of female die and has an actual industrial production application value, a tool is simple, and cost is saved.
Description
Technical field
The present invention relates to nonferrous materials processing engineering technology field, particularly a kind of be applicable to manufacture have deep camber profile or complicated variable curvature shape face can ageing strengthening aluminium alloy wallboard class A of geometric unitA based on autoclave can ageing strengthening aluminium alloy integral panel one-step moulding method.
Background technology
Overall structure wallboard because of its weight reduction, reducing production costs is widely used in the manufacturings such as Aero-Space and communications and transportation with advantages such as assembly work amounts.Creep age forming is exactly a kind of manufacture method growing up for this large-scale integral wallboard, it combines metal creep and aluminium alloy ageing strengthening characteristic, utilize aging temp to carry out the deformation of creep, there is security and repeatable and can realize the one-shot forming of wall panel parts.Creep age forming is because of shaping stress low (elastic range), thereby residual stress level is low, can reduce crackle and produce probability, improves endurance and stress corrosion resistant ability.But this lower shaping stress has also limited the crystallized ability of this method simultaneously, under the conventional institution of prescription of aluminium alloy, its creep compliance is generally lower than 1%.And actual Aero-Space integral panel member, as often thering is complicated variable curvature shape face or deep camber profile in the integral panel members such as wing wallboard, aircraft door, these members are difficult to realize one-shot forming with creep ageing, have weakened creep ageing technology in the advantage aspect production cost and cycle.In addition, existing many bibliographical informations are pointed out at present, and different creep stresses or mould shape face can affect the material property of creep age forming part.This member that causes curvature to change greatly there will be performance inhomogeneous after creep age forming, affects the service life of member.Visible, above-mentioned creep ageing one-shot forming is needed improvement badly in the shortcoming of member shape face and aspect of performance, otherwise is difficult to break through the development bottleneck that integral panel creep forming is manufactured.
Summary of the invention
The object of the present invention is to provide a kind of can be used for having deep camber profile or complicated variable curvature shape face can ageing strengthening aluminium alloy integral panel class A of geometric unitA one-step moulding method, when guaranteeing shaping, obtain uniform material property, and the residual stress of effectively controlling drip molding is in 50MPa.
Object of the present invention realizes by the following method: a kind of based on autoclave can ageing strengthening aluminium alloy integral panel one-step moulding method, comprise the following steps: first aluminum alloy slab is fixed on shaping dies, then vacuum sealing inserting in autoclave, the shape face of mould comprises deep camber scope shape face, in small curve scope shape face and middle curvature range shape face at least two kinds, slab is after inserting autoclave, slab is applied to aluminium alloy timeliness is temperature required pastes the required pressure of mould with member, after slab generation plastic deformation, keep temperature-resistant, reducing pressure to the required pressure of creep ageing then keeps until completion of prescription.
Described method, slab gross thickness is 1～50mm, slab type is without muscle structure or band muscle structure.
Described method, the curvature range of the shape face of shaping dies is determined by ratio R/t of the radius R of mould shape face curvature same area and the sheet metal thickness t of relevant position, 0<R/t<kE
t/ σ
stfor deep camber scope, R/t>kE
p/ σ
spfor small curve scope, kE
t/ σ
st<R/t<kE
p/ σ
spfor middle curvature range, wherein, k is the constant relevant to material and slab gross thickness, and scope is 0.3～0.8, can determine by the sample part forming test of equal thickness; E
tfor tensile modulus of elasticity, E
pfor modulus of elasticity in comperssion, σ
stfor material solid solution state tensile yield strength, σ
spfor material solid solution state compression yield strength.
Described method, the member position within the scope of described deep camber, material forming is plastic deformation, mold radius scope is 0.8R
*～R
*, R wherein
*for radius of target.
Described method, the member position within the scope of described small curve, material forming is creep forming, mold radius scope is 0.2R
*～0.5R
*, R wherein
*for radius of target.
Described method, the member position within the scope of described small curve, material forming is creep and plastic deformation acting in conjunction, mold radius scope is 0.5R
*～0.8R
*, R wherein
*for radius of target.
Described method, the aging temp providing in autoclave is 100～200 ℃.
Described method, it is 5～20Bar that described member pastes the required pressure of mould, temperature retention time is 0.5～2h.
Described method, the required pressure of described creep ageing is 1～5Bar, temperature retention time is 5～30h.
The present invention has following consideration in structural design: for complicated variable curvature shape surface member, first plastic deformation occurs at deep camber position, thereby discharged the internal stress at this position.For the second step creep forming stage provides more uniform interior state, form the approximate creep compliance that waits and be shaped, can eliminate the performance difference that internal stress causes, improve member integrated performance uniformity.For simple deep camber shape surface member, the mode that adopts this flow and creep simultaneously to carry out, can obviously reduce springback capacity, improves forming accuracy.
The invention has the advantages that: 1. first for the local plastic deformation at deep camber position, discharged the larger internal stress of component partial, can eliminate the component performance problem of non-uniform causing because of internal stress difference in creep ageing process; 2. the once-forming method that adopts plastic deformation to be combined with creep age forming, not only reduces the production cycle, also can obviously reduce final springback capacity, this for reducing large mold height, reduce production costs significant; 3. the residual stress of this process Forming Workpiece shapes workpiece much smaller than traditional plastic, and easy and simple to handle, and frock is simple, only needs a set of die to realize, cost-saving, has actual industrial production using value.
Indication aluminium alloy of the present invention can adopt diverse ways to prepare material requested and (or) parts.Creep ageing mould adopts Chinese patent 2011110209737.0: a kind of metal creep forming die.Embodiment of the present invention is used ATOS raster scanner to detect wallboard outer rim curved surface.Tensile tests at room is made standard tensile sample according to GB GB/T228-2002, and stretching experiment carries out on CSS-44100 universal material mechanical stretch machine, and draw speed is 2mm/min.Residual stress test adopts borehole strain method for releasing, according to the residual stress of CB3395-1992 sheet material measurement.
Below in conjunction with accompanying drawing, the invention will be further described.
Accompanying drawing explanation
Fig. 1 is for being processing step schematic diagram of the present invention;
Fig. 2 is fixture for forming schematic diagram of the present invention.
The specific embodiment
Below in conjunction with embodiment, be intended to further illustrate the present invention, and unrestricted the present invention.
In each embodiment, along shaping wallboard bending direction is equidistant, be divided into 5 sections, at every section, extract sample and carry out Mechanics Performance Testing and residual stress test.The definition list of references of resilience in the present invention " Ho K C; Lin J; Dean T A.Modelling of springback in creep forming thick aluminum sheets.International Journal of Plasticity; 2004,20 (4 – 5): 733-751. ".Be calculated as follows: η=(d
max/ d
0) * 100%, d in formula
maxfor after drip molding resilience with the maximum normal distance of mould, be d
0mould relevant position is apart from the distance of slab initial plane.Tensile test at room temperature standard adopts GB/T228-2002, and residual stress test adopts borehole strain method for releasing, and standard adopts CB3395-1992.
Embodiment 1
Wallboard material is 7050 aluminium alloys, and slab length is 850mm, and width is 240mm, and thickness is 10mm.Target shape face is 1000mm～15000mm continuous distributed along described wallboard length direction bending radius, is streamlined, adopts T6 institution of prescription.After 470 ℃ of solid solution 120min and shrend, slab is fixed on shaping dies, put into autoclave after having covered the fixture for forming that vacuum diaphragm forms vacuum sealing.Wherein mould shape face comprises deep camber scope: R/t=600/10～0.51 * (70.3 * 10
3/ 360)/10, small curve scope: R/t=0.51 * (73.8 * 10
3/ 320)/10～15000/10, middle curvature range: R/t=0.51 * (70.3 * 10
3/ 360)/10～0.51 * (73.8 * 10
3/ 320)/10.At autoclave, provide 120 ℃ of temperature and 4Bar pressure, make slab and mould laminating, now at deep camber part material, reach yield limit and plastic deformation occurs.Keep after 1h, tank internal pressure is down to 2Bar.After this in autoclave, temperature continues to keep 120 ℃ of temperature to continue 23h and carries out creep ageing.Finally, the air pressure in removal autoclave also reduces temperature, obtains required complicated variable curvature integral panel after slab resilience.
Embodiment 2
Wallboard material is 2124 aluminium alloys, and slab length is 1800mm, and width is 900mm, and thickness is 8mm.Target shape face is the ellipse that length semiaxis is respectively 378mm, 126mm along described wallboard length direction, wide crooked to straight nothing, adopts T6 institution of prescription.After 490 ℃ of solid solution 120min and shrend, slab is fixed on shaping dies, put into autoclave after having covered the fixture for forming that vacuum diaphragm forms vacuum sealing.Wherein mould shape face comprises deep camber scope: R/t=400/8～0.43 * (72 * 10
3/ 330)/8, small curve scope: R/t=0.43 * (74 * 10
3/ 300)/8～1200/8, middle curvature range: R/t=0.43 * (72 * 10
3/ 330)/8～0.43 * (74 * 10
3/ 300)/8.At autoclave, provide 190 ℃ of temperature and 8Bar pressure, make slab and mould laminating, now the deep camber part material at ellipsoid two ends reaches yield limit and plastic deformation occurs.Keep after 1h, tank internal pressure is down to 2Bar.After this in autoclave, temperature continues to keep 190 ℃ of temperature to continue 11h and carries out creep ageing.Finally, the air pressure in removal autoclave also reduces temperature, obtains required ellipsoid integral panel after slab resilience.
Embodiment 3
Wallboard material is 7475 aluminium alloys, and slab length is 1200mm, and width is 600mm.Web thickness is 2mm, and web one side is provided with the rib of high 18mm, thick 3mm.Rib is square-section and is grid and distributes, totally 16 single lattice, and each single lattice size is 300mm * 150mm.Target shape face is single-curvature bending radius 750mm along described wallboard width, adopts T76 institution of prescription.After 470 ℃ of solid solution 90min and shrend, slab is fixed on shaping dies, put into autoclave after having covered the fixture for forming that vacuum diaphragm forms vacuum sealing.Wherein mold radius is 650mm, curvature range: R/t=0.15 * (70 * 10 in the middle of belonging to
3/ 380)/20～0.15 * (73 * 10
3/ 310)/20.At autoclave, provide 120 ℃ of temperature and 5Bar pressure, make slab and mould laminating, now in the plastic deformation of slab generation part.Keep, after 1h, tank internal pressure being down to 3Bar.After this in autoclave, temperature continues to keep 120 ℃ of temperature 5h to carry out creep ageing, is then warming up to 175 ℃ and keeps 8h.Finally, the air pressure in removal autoclave also reduces temperature, obtains required deep camber band muscle integral panel after slab resilience.
Room-temperature mechanical property, springback capacity and the residual stress of material after table 1 embodiment of the present invention wallboard is shaped
Claims (9)
- One kind based on autoclave can ageing strengthening aluminium alloy integral panel one-step moulding method, comprise the following steps: first aluminum alloy slab is fixed on shaping dies, then vacuum sealing inserting in autoclave, it is characterized in that, the shape face of mould comprises deep camber scope shape face, in small curve scope shape face and middle curvature range shape face at least two kinds, slab is after inserting autoclave, slab is applied to aluminium alloy timeliness is temperature required pastes the required pressure of mould with member, after slab generation plastic deformation, keep temperature-resistant, reducing pressure to the required pressure of creep ageing then keeps until completion of prescription.
- 2. method according to claim 1, is characterized in that, slab gross thickness is 1～50mm, and slab type is without muscle structure or band muscle structure.
- 3. method according to claim 1, is characterized in that, the curvature range of the shape face of shaping dies is determined by ratio R/t of the radius R of mould shape face curvature same area and the sheet metal thickness t of relevant position, 0<R/t<kE t/ σ stfor deep camber scope, R/t>kE p/ σ spfor small curve scope, kE t/ σ st<R/t<kE p/ σ spfor middle curvature range, wherein, k is the constant relevant to material and slab gross thickness, and scope is 0.3～0.8; E tfor tensile modulus of elasticity, E pfor modulus of elasticity in comperssion, σ stfor material extending yield strength, σ spfor material compression yield strength.
- 4. method according to claim 1, is characterized in that, the member position within the scope of described deep camber, and material forming is plastic deformation, mold radius scope is 0.8R *～R *, R wherein *for radius of target.
- 5. method according to claim 1, is characterized in that, the member position within the scope of described small curve, and material forming is creep forming, mold radius scope is 0.2R *～0.5R *, R wherein *for radius of target.
- 6. method according to claim 1, is characterized in that, the member position within the scope of described small curve, and material forming is creep and plastic deformation acting in conjunction, mold radius scope is 0.5R *～0.8R *, R wherein *for radius of target.
- 7. method according to claim 1, is characterized in that, the aging temp providing in autoclave is 100～200 ℃.
- 8. method according to claim 1, is characterized in that, it is 5～20Bar that described member pastes the required pressure of mould, and temperature retention time is 0.5～2h.
- 9. method according to claim 1, is characterized in that, the required pressure of described creep ageing is 1～5Bar, and temperature retention time is 5～30h.
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|---|---|---|---|---|
| CN104190777A (en) * | 2014-09-26 | 2014-12-10 | 中南大学 | One-step shaping method for non-aging reinforced aluminum alloy whole wallboard based on autoclave |
| CN104438481A (en) * | 2014-11-28 | 2015-03-25 | 中南大学 | Method for manufacturing large-curvature aluminum alloy integral wall board component |
| CN104561848A (en) * | 2014-12-26 | 2015-04-29 | 中国航空工业集团公司北京航空制造工程研究所 | Creep age forming technological method |
| CN105779748A (en) * | 2014-12-24 | 2016-07-20 | 北京有色金属研究总院 | Aging strengthened alloy ring creep aging shape correcting method |
| CN106978578A (en) * | 2017-05-18 | 2017-07-25 | 中南大学 | A kind of aluminium alloy plate creep age forming method |
| CN107988569A (en) * | 2017-10-18 | 2018-05-04 | 中国航发北京航空材料研究院 | A kind of age forming method of aluminium lithium alloy with muscle integral panel |
| CN108380736A (en) * | 2018-04-28 | 2018-08-10 | 中南大学 | A kind of device for complex curvatures aluminium alloy element vacuum creep age forming |
| CN108637081A (en) * | 2018-04-28 | 2018-10-12 | 中南大学 | A kind of method of complex curvatures aluminium alloy element vacuum creep age forming |
| CN110026478A (en) * | 2019-04-30 | 2019-07-19 | 重庆三峡学院 | The method and apparatus of the compound timeliness progressive molding of Vibration Creep based on air pressure-loading |
| CN110252881A (en) * | 2019-06-28 | 2019-09-20 | 中南大学 | A kind of creep age forming regulation method |
| CN111122316A (en) * | 2019-12-13 | 2020-05-08 | 中国航空工业集团公司西安飞机设计研究所 | Device for eliminating residual stress of aviation metal part and examining aging performance |
| CN111122315A (en) * | 2019-12-13 | 2020-05-08 | 中国航空工业集团公司西安飞机设计研究所 | Aging performance assessment method for eliminating residual stress of aviation metal part |
| CN111218633A (en) * | 2020-02-18 | 2020-06-02 | 南昌航空大学 | Method and device for press aging forming of plate |
| EP3680037A1 (en) * | 2019-01-11 | 2020-07-15 | Embraer S.A. | Method for producing creep age formed aircraft components |
| CN112570537A (en) * | 2020-10-27 | 2021-03-30 | 航天材料及工艺研究所 | Rubber padding material assisted creep aging precision forming method for aluminum alloy thin-wall component |
| CN113976707A (en) * | 2021-11-03 | 2022-01-28 | 西北工业大学 | Compound forming method for aluminum alloy large-curvature complex wallboard component |
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| CN104190777B (en) * | 2014-09-26 | 2016-06-29 | 中南大学 | A kind of once-forming method of the integral panel of aluminium alloy without ageing strengthening based on autoclave |
| CN104438481A (en) * | 2014-11-28 | 2015-03-25 | 中南大学 | Method for manufacturing large-curvature aluminum alloy integral wall board component |
| CN105779748A (en) * | 2014-12-24 | 2016-07-20 | 北京有色金属研究总院 | Aging strengthened alloy ring creep aging shape correcting method |
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| CN108380736B (en) * | 2018-04-28 | 2020-01-31 | 中南大学 | device for vacuum creep age forming of aluminum alloy member with complex curvature |
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| CN111434418A (en) * | 2019-01-11 | 2020-07-21 | 埃姆普里萨有限公司 | Method for producing creep-age-formed aircraft components |
| EP3680037A1 (en) * | 2019-01-11 | 2020-07-15 | Embraer S.A. | Method for producing creep age formed aircraft components |
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| CN110026478B (en) * | 2019-04-30 | 2024-05-03 | 中国民用航空飞行学院 | Method and device for vibration creep composite aging incremental forming based on pneumatic loading |
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| CN111122315A (en) * | 2019-12-13 | 2020-05-08 | 中国航空工业集团公司西安飞机设计研究所 | Aging performance assessment method for eliminating residual stress of aviation metal part |
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| CN111122316B (en) * | 2019-12-13 | 2022-11-18 | 中国航空工业集团公司西安飞机设计研究所 | Device for eliminating residual stress of aviation metal part and examining aging performance |
| CN111218633A (en) * | 2020-02-18 | 2020-06-02 | 南昌航空大学 | Method and device for press aging forming of plate |
| CN112570537A (en) * | 2020-10-27 | 2021-03-30 | 航天材料及工艺研究所 | Rubber padding material assisted creep aging precision forming method for aluminum alloy thin-wall component |
| CN112570537B (en) * | 2020-10-27 | 2022-11-11 | 航天材料及工艺研究所 | Creep aging precision forming method for aluminum alloy thin-wall component assisted by rubber padding |
| CN113976707A (en) * | 2021-11-03 | 2022-01-28 | 西北工业大学 | Compound forming method for aluminum alloy large-curvature complex wallboard component |
| CN113976707B (en) * | 2021-11-03 | 2023-09-01 | 西北工业大学 | Composite forming method for aluminum alloy large-curvature complex wallboard member |
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